I.S.A. 571 (isa571-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 571 (isa571-il) Reynolds number: 100,000 Max Cl/Cd: 54.34 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa571-il-100000-n5.txt Download as CSV file: xf-isa571-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 571
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3973 0.10616 0.10128 -0.0236 1.0000 0.0383
-8.750 -0.3989 0.10339 0.09859 -0.0241 1.0000 0.0384
-8.500 -0.4013 0.10063 0.09590 -0.0243 1.0000 0.0384
-8.250 -0.4004 0.09742 0.09275 -0.0254 1.0000 0.0384
-8.000 -0.3979 0.09402 0.08940 -0.0268 1.0000 0.0384
-7.500 -0.3916 0.08519 0.08059 -0.0243 1.0000 0.0291
-7.250 -0.3883 0.08200 0.07744 -0.0240 1.0000 0.0280
-7.000 -0.3843 0.07851 0.07398 -0.0256 1.0000 0.0276
-6.750 -0.3782 0.07479 0.07028 -0.0277 1.0000 0.0276
-6.500 -0.3696 0.07085 0.06633 -0.0303 1.0000 0.0279
-6.250 -0.3584 0.06673 0.06217 -0.0329 1.0000 0.0280
-6.000 -0.3447 0.06248 0.05786 -0.0355 1.0000 0.0279
-5.750 -0.3289 0.05815 0.05344 -0.0379 1.0000 0.0275
-5.500 -0.3101 0.05363 0.04878 -0.0405 1.0000 0.0271
-5.250 -0.2884 0.04896 0.04392 -0.0431 1.0000 0.0269
-5.000 -0.2641 0.04420 0.03889 -0.0455 1.0000 0.0270
-4.750 -0.2360 0.03905 0.03333 -0.0479 1.0000 0.0283
-4.500 -0.2038 0.03307 0.02669 -0.0504 1.0000 0.0304
-4.250 -0.1804 0.03132 0.02476 -0.0506 1.0000 0.0320
-4.000 -0.1513 0.02825 0.02119 -0.0515 1.0000 0.0344
-3.750 -0.1198 0.02527 0.01750 -0.0524 1.0000 0.0400
-3.500 -0.0849 0.02364 0.01554 -0.0541 0.9977 0.0448
-3.250 -0.0370 0.02195 0.01340 -0.0583 0.9907 0.0545
-3.000 0.0106 0.02060 0.01165 -0.0622 0.9822 0.0643
-2.750 0.0537 0.01955 0.01041 -0.0652 0.9739 0.0694
-2.500 0.0944 0.01884 0.00954 -0.0678 0.9666 0.0763
-2.250 0.1292 0.01812 0.00875 -0.0691 0.9578 0.0793
-2.000 0.1657 0.01744 0.00800 -0.0707 0.9496 0.0830
-1.750 0.2028 0.01682 0.00736 -0.0724 0.9407 0.0872
-1.500 0.2361 0.01634 0.00686 -0.0733 0.9293 0.0932
-1.250 0.2701 0.01589 0.00642 -0.0744 0.9172 0.1044
-1.000 0.3036 0.01540 0.00591 -0.0753 0.9038 0.1192
-0.750 0.3364 0.01491 0.00548 -0.0760 0.8881 0.1439
-0.500 0.3709 0.01427 0.00515 -0.0773 0.8705 0.2343
0.250 0.4719 0.01204 0.00434 -0.0789 0.7938 1.0000
0.500 0.5077 0.01202 0.00407 -0.0799 0.7562 1.0000
0.750 0.5402 0.01213 0.00389 -0.0803 0.7149 1.0000
1.000 0.5696 0.01234 0.00384 -0.0802 0.6739 1.0000
1.250 0.5971 0.01263 0.00386 -0.0798 0.6358 1.0000
1.500 0.6232 0.01295 0.00395 -0.0793 0.5987 1.0000
1.750 0.6487 0.01330 0.00408 -0.0787 0.5629 1.0000
2.000 0.6739 0.01363 0.00423 -0.0781 0.5307 1.0000
2.250 0.6990 0.01398 0.00439 -0.0775 0.5021 1.0000
2.500 0.7241 0.01433 0.00459 -0.0770 0.4772 1.0000
2.750 0.7493 0.01470 0.00484 -0.0765 0.4575 1.0000
3.000 0.7748 0.01505 0.00511 -0.0760 0.4408 1.0000
3.250 0.8002 0.01541 0.00541 -0.0756 0.4257 1.0000
3.500 0.8255 0.01579 0.00575 -0.0752 0.4107 1.0000
3.750 0.8506 0.01616 0.00610 -0.0748 0.3962 1.0000
4.000 0.8757 0.01654 0.00646 -0.0743 0.3825 1.0000
4.250 0.9007 0.01693 0.00687 -0.0739 0.3700 1.0000
4.500 0.9260 0.01729 0.00730 -0.0735 0.3586 1.0000
4.750 0.9512 0.01768 0.00775 -0.0731 0.3479 1.0000
5.000 0.9761 0.01808 0.00822 -0.0726 0.3367 1.0000
5.250 1.0004 0.01849 0.00872 -0.0721 0.3236 1.0000
5.500 1.0244 0.01889 0.00920 -0.0715 0.3093 1.0000
5.750 1.0483 0.01932 0.00972 -0.0709 0.2958 1.0000
6.000 1.0721 0.01974 0.01026 -0.0703 0.2815 1.0000
6.250 1.0957 0.02017 0.01084 -0.0697 0.2667 1.0000
6.500 1.1184 0.02058 0.01141 -0.0689 0.2444 1.0000
6.750 1.1385 0.02111 0.01183 -0.0679 0.2073 1.0000
7.000 1.1585 0.02185 0.01249 -0.0669 0.1810 1.0000
7.250 1.1774 0.02279 0.01335 -0.0658 0.1518 1.0000
7.500 1.1959 0.02385 0.01429 -0.0647 0.1008 1.0000
7.750 1.2064 0.02593 0.01588 -0.0627 0.0405 1.0000
8.000 1.2178 0.02783 0.01770 -0.0605 0.0292 1.0000
8.250 1.2282 0.02970 0.01975 -0.0583 0.0246 1.0000
8.500 1.2413 0.03112 0.02145 -0.0563 0.0226 1.0000
8.750 1.2515 0.03270 0.02330 -0.0539 0.0214 1.0000
9.000 1.2590 0.03440 0.02525 -0.0514 0.0203 1.0000
9.250 1.2636 0.03619 0.02727 -0.0486 0.0192 1.0000
9.500 1.2639 0.03804 0.02930 -0.0454 0.0181 1.0000
9.750 1.2622 0.04013 0.03156 -0.0423 0.0172 1.0000
10.000 1.2583 0.04252 0.03412 -0.0394 0.0164 1.0000
10.250 1.2535 0.04518 0.03695 -0.0370 0.0159 1.0000
10.500 1.2492 0.04806 0.03998 -0.0349 0.0155 1.0000
10.750 1.2458 0.05118 0.04324 -0.0332 0.0152 1.0000
11.000 1.2438 0.05449 0.04672 -0.0318 0.0149 1.0000
11.250 1.2421 0.05805 0.05043 -0.0306 0.0147 1.0000
11.500 1.2403 0.06143 0.05404 -0.0301 0.0146 1.0000
11.750 1.2364 0.06517 0.05801 -0.0300 0.0145 1.0000
12.000 1.2307 0.06929 0.06236 -0.0304 0.0144 1.0000
12.250 1.2231 0.07381 0.06712 -0.0315 0.0143 1.0000
12.500 1.2138 0.07877 0.07231 -0.0331 0.0142 1.0000
12.750 1.2031 0.08417 0.07794 -0.0353 0.0141 1.0000
13.000 1.1909 0.09004 0.08403 -0.0381 0.0141 1.0000
13.250 1.1778 0.09634 0.09053 -0.0413 0.0141 1.0000
13.500 1.1638 0.10307 0.09745 -0.0449 0.0141 1.0000
13.750 1.1493 0.11021 0.10478 -0.0489 0.0141 1.0000
14.000 1.1344 0.11777 0.11251 -0.0533 0.0142 1.0000
14.250 1.1194 0.12570 0.12059 -0.0580 0.0143 1.0000
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Polar data table (+)
Polar graphs
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